CA2514385A1 - Recessed engine nacelle - Google Patents

Recessed engine nacelle Download PDF

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Publication number
CA2514385A1
CA2514385A1 CA002514385A CA2514385A CA2514385A1 CA 2514385 A1 CA2514385 A1 CA 2514385A1 CA 002514385 A CA002514385 A CA 002514385A CA 2514385 A CA2514385 A CA 2514385A CA 2514385 A1 CA2514385 A1 CA 2514385A1
Authority
CA
Canada
Prior art keywords
recess
nacelle according
nacelle
skin
exhaust outlet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA002514385A
Other languages
French (fr)
Other versions
CA2514385C (en
Inventor
Jean-Pierre Lair
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nordam Group LLC
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of CA2514385A1 publication Critical patent/CA2514385A1/en
Application granted granted Critical
Publication of CA2514385C publication Critical patent/CA2514385C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B64C7/02—Nacelles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Silencers (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Wind Motors (AREA)

Abstract

A gas turbine engine nacelle (16) includes an inner skin (38) surrounded by a radially outer skin (40). The inner skin (38) terminates at an exhaust outlet (44). The outer skin (40) terminates at a recess (46) in the inner skin (38) extending into a closed cavity (48) under the outer skin (40).

Claims (20)

1. A gas turbine engine nacelle comprising:
an inner skin terminating at an exhaust outlet; and a radially outer skin surrounding said inner skin, and terminating at a recess in said inner skin extending into a closed cavity under said outer skin.
2. A nacelle according to claim 1 wherein said outer and inner skins converge aft and are axially interrupted by said recess therebetween.
3. A nacelle according to claim 2 wherein said cavity converges aft to said recess.
4. A nacelle according to claim 3 wherein said cavity includes a radial frame bridging said inner and outer skins forward of said recess.
5. A nacelle according to claim 2 wherein said inner skin is generally cylindrical under said recess.
6. A nacelle according to claim 5 wherein said recess blends into said inner skin aft thereof, and said outer and inner skins are axially coextensive across said recess in a common convergence thereacross.
7. A nacelle according to claim 2 wherein said recess extends in axial length over a minor portion of the distance to said exhaust outlet.
8. A nacelle according to claim 7 wherein said recess axial length is about 12 percent of the distance between the aft ends of said inner and outer skins.
9. A nacelle according to claim 2 wherein said cavity has an arcuate inlet at the aft end of said outer skin, with a flow area being a minor portion of the flow area for said exhaust outlet.
10. A nacelle according to claim 9 wherein said flow area for said cavity inlet is less than or equal to about 10 percent of the flow area for said exhaust outlet.
11. A nacelle according to claim 2 comprising a short nacelle surrounding a forward portion of a core engine to define a fan bypass duct therebetween terminating at said exhaust outlet disposed upstream from a separate outlet of said core engine.
12. A nacelle according to claim 2 comprising a long nacelle surrounding a core engine to define a common exhaust outlet at the aft end thereof for both core exhaust and fan bypass exhaust.
13. A gas turbine engine nacelle comprising:

an inner skin terminating at a converging boattail portion thereof having a nozzle outlet at an aft end thereof; and a radially outer skin surrounding said inner skin forward of said boattail portion, and converging to a recess in said inner skin disposed upstream from said nozzle outlet, with said recess extending forward into a closed cavity under said outer skin.
14. A nacelle according to claim 13 wherein said cavity includes a radial frame bridging said inner and outer skins forward of said recess.
15. A nacelle according to claim 14 wherein said inner skin is generally cylindrical under said recess.
16. A nacelle according to claim 15 wherein said recess blends into said boattail portion aft thereof, and said outer and inner skins are axially coextensive across said recess in a common convergence thereacross.
17. A nacelle according to claim 16 wherein said recess extends in axial length over a minor portion of the distance to said exhaust outlet.
18. A nacelle according to claim 17 wherein said cavity has an arcuate inlet at the aft end of said outer skin, with a flow area being a minor portion of the flow area for said exhaust outlet.
19. A nacelle according to claim 18 wherein said recess axial length is about 12 percent of the distance between the aft ends of said inner and outer skins.
20. A nacelle according to claim 19 wherein said flow area for said cavity inlet is less than or equal to about 10 percent of the flow area for said exhaust outlet.
CA2514385A 2003-02-21 2004-02-19 Recessed engine nacelle Expired - Fee Related CA2514385C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US44908103P 2003-02-21 2003-02-21
US60/449,081 2003-02-21
PCT/US2004/004881 WO2005024218A2 (en) 2003-02-21 2004-02-19 Recessed engine nacelle

Publications (2)

Publication Number Publication Date
CA2514385A1 true CA2514385A1 (en) 2005-03-17
CA2514385C CA2514385C (en) 2011-05-03

Family

ID=34272384

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2514385A Expired - Fee Related CA2514385C (en) 2003-02-21 2004-02-19 Recessed engine nacelle

Country Status (5)

Country Link
US (1) US6945031B2 (en)
EP (1) EP1595067B1 (en)
BR (1) BRPI0407599B8 (en)
CA (1) CA2514385C (en)
WO (1) WO2005024218A2 (en)

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US8997454B2 (en) * 2002-03-20 2015-04-07 The Regents Of The University Of California Turbofan engine noise suppression using fan flow deflector
EP1831073A2 (en) * 2004-12-22 2007-09-12 Aurora Flight Sciences Corporation System and method for utilizing stored electrical energy for vtol aircraft thrust enhancement and attitude control
US20110101158A1 (en) * 2005-03-29 2011-05-05 The Boeing Company Thrust Reversers Including Monolithic Components
US7571527B2 (en) * 2005-03-29 2009-08-11 The Boeing Company Mandrel for fabrication of a monolithic composite nacelle panel
US7690190B2 (en) 2005-05-11 2010-04-06 The Boeing Company Aircraft systems including cascade thrust reversers
US7559507B2 (en) * 2005-06-27 2009-07-14 The Boeing Company Thrust reversers including locking assemblies for inhibiting deflection
US7600371B2 (en) 2005-10-18 2009-10-13 The Boeing Company Thrust reversers including support members for inhibiting deflection
FR2902758B1 (en) * 2006-06-21 2009-04-10 Airbus France Sas PROPELLANT AIRCRAFT ASSEMBLY COMPRISING AN EJECTION DUCT WITH A LEAK EDGE OFFSET
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US7681399B2 (en) * 2006-11-14 2010-03-23 General Electric Company Turbofan engine cowl assembly and method of operating the same
US7673458B2 (en) * 2006-11-14 2010-03-09 General Electric Company Turbofan engine nozzle assembly and method for operating the same
US7726116B2 (en) * 2006-11-14 2010-06-01 General Electric Company Turbofan engine nozzle assembly and method of operating same
US8657567B2 (en) * 2007-05-29 2014-02-25 United Technologies Corporation Nacelle compartment plenum for bleed air flow delivery system
US7708230B2 (en) * 2007-05-29 2010-05-04 United Technologies Corporation Flow distribution system for inlet flow control
US8312728B2 (en) * 2007-06-28 2012-11-20 United Technologies Corporation Generator with separate oil system for improved nacelle performance
US9091214B2 (en) * 2007-06-28 2015-07-28 United Technologies Corporation Reduced gearbox size by separate electrically powered engine oil system
US9759087B2 (en) 2007-08-08 2017-09-12 Rohr, Inc. Translating variable area fan nozzle providing an upstream bypass flow exit
CN101939528B (en) * 2007-08-08 2013-07-24 罗尔股份有限公司 Variable area fan nozzle with bypass flow
US7735778B2 (en) * 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US7762086B2 (en) * 2008-03-12 2010-07-27 United Technologies Corporation Nozzle extension assembly for ground and flight testing
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US9188025B2 (en) * 2008-11-26 2015-11-17 Mra Systems, Inc. Apparatus for facilitating access to a nacelle interior
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Also Published As

Publication number Publication date
US6945031B2 (en) 2005-09-20
BRPI0407599A (en) 2006-02-14
BRPI0407599B1 (en) 2015-10-13
US20040164204A1 (en) 2004-08-26
EP1595067B1 (en) 2016-09-28
EP1595067A2 (en) 2005-11-16
WO2005024218A3 (en) 2005-09-01
BRPI0407599B8 (en) 2017-04-25
EP1595067A4 (en) 2011-11-23
CA2514385C (en) 2011-05-03
WO2005024218A2 (en) 2005-03-17

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Effective date: 20210219